Intermediate structure for independently de-mountable propulsion components

ABSTRACT

An intermediate structure of an aircraft configured to mechanically attach an engine core and an engine fan module to each other and to the aircraft. The intermediate structure may have a ring-shaped portion and/or an elongated mount beam extending substantially perpendicularly from the ring-shaped portion. The ring-shaped portion may have a forward edge and an aft edge opposite of the forward edge, and may include a first attachment portion for attaching to a flange of the engine core, a second attachment portion for attaching to a flange of the engine fan module, and a mounting portion configured for mounting directly to a pylon or airframe of an aircraft. The engine core and/or the engine fan module may independently mechanically attach to and detach from the intermediate structure. The intermediate structure may have a gearbox mounted thereto for interfacing with rotary components of the engine core and the engine fan module.

RELATED APPLICATIONS

This divisional non-provisional application claims priority benefit of aparent non-provisional application entitled, “Intermediate Structure forIndependently De-mountable Propulsion Components,” Ser. No. 13/552,001,filed Jul. 18, 2012 and incorporated by reference herein in itsentirety.

BACKGROUND

A typical aircraft propulsion system may include an engine having anengine fan module and an engine core or hot section, as well as anacelle inlet and/or a primary exhaust plug and nozzle. The enginecomponents occasionally require maintenance, removal, and/orreplacement.

Aircraft propulsion systems mounted on aft fuselage, or empennage, are achallenge to maintenance personnel for ready access and ergonomics. Tallstands are generally required to gain access to these propulsionsystems. For example, in single-aisle, 150-seat class aircrafts withopen-rotor propulsion systems, the rotor diameters may exceed fourteenfeet in diameter. Positioned high on the aft fuselage, theseinstallations are a considerable distance above the ground and thereforedifficult to reach.

It is also difficult to perform an engine change on a high-mountedpropulsion installation, partially due to the size and weight of thepropulsion unit. In current aircraft propulsion systems, even if onlythe engine core requires off-wing maintenance, the entire aircraftpropulsion system must be removed. This requires robust ground supportequipment (GSE) and navigating the cumbersome fan module with itsfourteen foot diameter rotor disc around the aircrafts nearby pylon,tail, and fuselage structures.

Accordingly, there is a need for an improved method of mounting anddemounting an aircraft propulsion system that overcomes the limitationsof the prior art.

SUMMARY

This summary is provided to introduce a selection of concepts in asimplified form that are further described below in the detaileddescription. This summary is not intended to identify key features oressential features of the claimed subject matter, nor is it intended tobe used to limit the scope of the claimed subject matter. Other aspectsand advantages of the present invention will be apparent from thefollowing detailed description of the preferred embodiments and theaccompanying drawing figures.

Embodiments of the present invention solve the above-mentioned problemsand provide a distinct advantage in the art of aircraft propulsionsystem mounting. More particularly, embodiments of the present inventionprovide an intermediate structure of an aircraft configured tomechanically attach an engine core and an engine fan module to eachother and the aircraft. The intermediate structure may have a firstattachment portion, a second attachment portion, and a mounting portion.The first attachment portion may be configured for attaching to a flangeof the engine core and the second attachment portion may be configuredfor attaching to a flange of the engine fan module. The mounting portionmay be configured for mounting directly to a pylon or airframe of anaircraft.

In another embodiment of the invention, the intermediate structure maycomprise a ring-shaped portion made of a rigid material and having aforward edge and an aft edge opposite of the forward edge. Thering-shaped portion may comprise a first attachment portion, a secondattachment portion, and a mounting portion. The first attachment portionmay be configured for attaching to a flange of the engine core and thesecond attachment portion may be configured for attaching to a flange ofthe engine fan module. The mounting portion may be configured formounting directly to a pylon or airframe of an aircraft. Furthermore,the intermediate structure may comprise an elongated mount beam having afirst end integrally formed with and extending substantiallyperpendicular from the forward or aft edge of the ring-shaped portionand a second end opposite of the first end for structurally supportingthe engine core.

Another embodiment of the invention includes a method of coupling anddecoupling an engine core with an engine fan module via an intermediatestructure of an aircraft. The intermediate structure may have aring-shaped portion made of a rigid material and mounted directly to apylon or airframe of the aircraft. The method may include the steps ofmechanically attaching the engine core to the intermediate structure ata first edge of the intermediate structure and mechanically attachingthe engine fan module to the intermediate structure at a second edge ofthe intermediate structure. The second edge of the intermediatestructure may be opposite of the first edge. Finally, the is method mayinclude step of mechanically disconnecting and removing one of theengine core and the engine fan module from the intermediate structurewhile another one of the engine core and the engine fan module remainsmechanically attached to and supported on the aircraft by theintermediate structure.

BRIEF DESCRIPTION OF THE DRAWING FIGURES

A preferred embodiment of the present invention is described in detailbelow with reference to the attached drawing figures, wherein:

FIG. 1 is an exploded perspective view of an aircraft pylon, apropulsion system having a “pusher” configuration, and an intermediatestructure constructed in accordance with an embodiment of the presentinvention;

FIG. 2 is a perspective view of the pylon, propulsion system, andintermediate structure of FIG. 1, with an engine core of the propulsionsystem detached from the intermediate structure;

FIG. 3 is a perspective view of the pylon, propulsion system, andintermediate structure of FIG. 1, with an engine fan module of thepropulsion system detached from the intermediate structure;

FIG. 4 a perspective view of the pylon, propulsion system, andintermediate structure of FIG. 1 with both the engine core and theengine fan module attached to and supported by the intermediatestructure;

FIG. 5 is a perspective view of an alternative embodiment of theintermediate structure and propulsion system of FIGS. 1-4 arranged in a“puller” configuration;

FIG. 6 is an exploded perspective view of the intermediate structure andpropulsion system of FIG. 5;

FIG. 7 is a perspective view of another alternative embodiment of theintermediate structure and the propulsion system of FIGS. 1-4, with thepropulsion system comprising an empennage-mounted ducted turbo fan;

FIG. 8 is an exploded perspective view of the intermediate structure andpropulsion system of FIG. 7;

FIG. 9 is a perspective view of another alternative embodiment of theintermediate structure and the propulsion system of FIGS. 1-4, with thepropulsion system comprising an under-wing mounted ducted turbo fan;

FIG. 10 is a perspective view of the intermediate structure andpropulsion system of FIG. 9 with the engine core of the propulsionsystem detached from the intermediate structure;

FIG. 11 is a perspective view of yet another alternative embodiment ofthe intermediate structure and the propulsion system of FIGS. 1-4, withthe propulsion system having a ducted prop-fan installation;

FIG. 12 is a fragmentary side view of the propulsion system and a firstembodiment of the intermediate structure of FIG. 1 configured todetachably attach to both the engine fan module and the engine core;

FIG. 13 is a fragmentary side view of the propulsion system and a secondembodiment of the intermediate structure of FIG. 1 configured todetachably attach to both the engine fan module and the engine core;

FIG. 14 is a fragmentary side view of the propulsion system and a thirdembodiment of the intermediate structure of FIG. 1 integrally andpermanently attached to the engine fan module and configured todetachably attach to the engine core;

FIG. 15 is a fragmentary side view of the propulsion system and a fourthembodiment of the intermediate structure of FIG. 1 integrally andpermanently attached to the engine fan module and configured todetachably attach to the engine core;

FIG. 16 is a perspective view of the intermediate structure of FIG. 1;and

FIG. 17 is a perspective view of an alternative embodiment of theintermediate structure of FIG. 16.

The drawing figures do not limit the present invention to the specificembodiments disclosed and described herein. The drawings are notnecessarily to scale, emphasis instead being placed upon clearlyillustrating the principles of the invention.

DETAILED DESCRIPTION

The following detailed description of the invention references theaccompanying drawings that illustrate specific embodiments in which theinvention can be practiced. The embodiments are intended to describeaspects of the invention in sufficient detail to enable those skilled inthe art to practice the invention. Other embodiments can be utilized andchanges can be made without departing from the scope of the presentinvention. The following detailed description is, therefore, not to betaken in a limiting sense. The scope of the present invention is definedonly by the appended claims, along with the full scope of equivalents towhich such claims are entitled.

In this description, references to “one embodiment”, “an embodiment”, or“embodiments” mean that the feature or features being referred to areincluded in at least one embodiment of the technology. Separatereferences to “one embodiment”, “an embodiment”, or “embodiments” inthis description do not necessarily refer to the same embodiment and arealso not mutually exclusive unless so stated and/or except as will bereadily apparent to those skilled in the art from the description. Forexample, a feature, structure, act, etc. described in one embodiment mayalso be included in other embodiments, but is not necessarily included.Thus, the present technology can include a variety of combinationsand/or integrations of the embodiments described herein.

An aircraft propulsion system 10 constructed in accordance withembodiments of the present invention is shown in FIGS. 1-15 and includesan engine fan module 12 and an engine core 14 which are attached andsupported by an intermediate structure 16 to an airframe or pylon 18 ofan aircraft. In some embodiments of the invention, portions of theaircraft propulsion system 10 may be surrounded by a fan case 20 with anacelle inlet 22 attached thereto, as illustrated in FIGS. 7-10.Additionally, the aircraft propulsion system 10 may comprise a primaryexhaust plug and nozzle 24 attached to an aft turbine frame of theengine core 14 or the fan module 12.

The propulsion system 10 may use any propulsion configuration known inthe art, such as an empennage-mounted, open-rotor installation commonlyknown as a “pusher” configuration which has the engine core 14 locatedforward of the engine fan module 12, as illustrated in FIGS. 1-4.Alternatively, the propulsion system 10 may be an empennage-mounted,open-rotor installation commonly known as a “puller” configuration whichhas the engine core 14 located aftward of the engine fan module 12, asillustrated in FIGS. 5-6. In both of these empennage-mounted, open rotorinstallations, the engine fan module 12 may be a single shaft ring gearcontra-rotating fan module or a twin shaft contra-rotating fan module.In another alternative embodiment of the invention, the propulsionsystem 10 may be an empennage mounted ducted turbofan having the fancase 20 at least partially surrounding the engine fan module 12 and thenacelle inlet 22 attached to the fan case 20, as illustrated in FIGS.7-8. Furthermore, in another configuration of the invention, thepropulsion system 10 may be an underwing mounted ducted turbofan havingthe fan case 20 and the nacelle inlet 22 illustrated in FIGS. 9-10. Inyet another configuration, the propulsion system 10 may be a ductedprop-fan installation, as illustrated in FIG. 10.

The engine fan module 12 may be any aircraft engine fan module and maycomprise a support frame 26 and/or shaft and one or more sets of blades28 extending radially from and/or rotatably supported relative to thesupport frame or shaft. The support frame 26 or shaft may also compriseone or more mounting provisions 30 or flanges extending therefrom andconfigured to be mechanically attached to the intermediate structure 16,as later described herein. In some embodiments of the invention, theintermediate structure 16 suspends the engine fan module 12 in aconfiguration such that the blades 28 are forward or aftward of thepylon 18 to which the intermediate structure 16 attaches.

The engine core 14 may be any aircraft engine core and may also bereferred to as a hot section of an aircraft engine. The engine core 14may generally comprise a compressor, a combustor, a turbine, the primaryexhaust plug or nozzle 24 and/or any other engine core components knownin the art. The engine core may also comprise one or more mountingprovisions 32 or flanges extending therefrom and configured to bemechanically attached to the intermediate structure 16, as laterdescribed herein.

The intermediate structure 16, as illustrated in FIGS. 12-16 maycomprise a rigid ring portion 34 having an axial thickness bounded by afirst circumferential edge 36 and a second circumferential edge 38opposite of the first circumferential edge. The ring portion 34 may becylindrical or ring-shaped and may extend 360 degrees or, in analternative embodiment of the invention, may be a partial structuralring only extending circumferentially as far as necessary to connect toan interconnect structure, as later described herein. The first andsecond circumferential edges 36,38 may be opposing surfaces of the ringwith a width in a radial direction relative to the ring portion. Thefirst and second circumferential edges 36,38 may be configured tointerface with the mounting provisions 30,32 of the fan assembly 12and/or the engine core 14. For instance, in some embodiments of theinvention, holes may be drilled into the first and secondcircumferential edges 36,38 or surfaces sized for bolts or attachmentpins to be inserted therein. Thus, the fan assembly 12 and the enginecore 14 may be bolted to the ring portion 34 of the intermediatestructure 16.

In some embodiments of the invention, the intermediate structure 16 mayalso comprise a first flange 40 extending from the first circumferentialedge 36 of the ring portion 34 and configured to align with the mountingprovisions 30,32 of the engine fan module 12 and/or the engine core 14.Additionally, the intermediate structure 16 may comprise a second flange42 extending from the second circumferential edge 38 of the ring portion34 and configured to align with the mounting provisions 30,32 of theengine fan module 12 and/or the engine core 14. The first and secondflanges 40,42, as illustrated in FIGS. 12-13, may be bolted or otherwisemechanically connected to the mounting provisions 30,32 of the fanmodule 12 and the engine core 14. For example, the fan module 12 may bebolted to the intermediate structure 16 directly by a circular patternof bolts similar to the joint of prior art engine core to fan moduleinterfaces. Likewise, the engine core 14 may be bolted to theintermediate structure 16 directly by a circular pattern of bolts.

In some embodiments of the invention, as illustrated in FIG. 12, thefirst and second flanges 40,42 may generally extend radially inward fromthe ring portion 34, toward a center axis of the ring portion 34.Additionally, the first and second flanges 40,42 may have first portions44 angled slightly away from each other in the direction of axialthickness of the ring portion 34, and second portions 46 substantiallyparallel with each other and with the first and second circumferentialedges 36,38 of the ring portion 34. In another alternative embodiment ofthe invention, the ring portion 34 may be attached to an interconnectstructure 48 via interconnect links 50 extending radially inward towarda center axis of the ring portion 34, as in FIG. 13. The interconnectstructure 48 may also be cylindrical or ring-shaped. In this embodimentof the invention, the first and second flanges 40,42 may extend radiallyoutward from first and second edges of the interconnect structure 48 toconnect the fan module 12 and the engine core 14 to the interconnectstructure 48 supported by the ring portion 34 via the interconnect links50, as illustrated in FIG. 13. Furthermore, in this embodiment of theinvention, the ring portion 34 may be a partial structural ring onlyextending around a circumference as far as necessary to connect to theinterconnect structure 48.

In some alternative embodiments of the invention, the ring portion 34and/or interconnect structure 48 may be permanently fixed to the fanmodule 12, as illustrated in FIGS. 14-15. This configuration would allowfor the removal of the engine core 14 while the fan module 12 remainsfixed to the pylon 18. However, this configuration is limited in thatthe engine core 14 could not be supported by the pylon 18 if the fanmodule 12 was removed therefrom without the use of temporary bracing.

The intermediate structure 16 may further comprise and/or be attached toan elongated mount beam 52, as illustrated in FIGS. 16-17. The mountbeam 52 may extend substantially perpendicular from the ring portion 34at the first or second circumferential edge 36,38. In some embodimentsof the invention, the mount beam 52 is integrally formed with the ringportion 34 and is of one-piece construction therewith. For example, asillustrated in FIG. 16, a substantially triangular or tapering section54 may extend from a portion of the first or second circumferential edge36,38 to the mounting beam 52 and may have a slightly curved surfacecorresponding to the curve of the ring portion 34. Likewise, themounting beam 52 extending from the substantially triangular or taperingsection 54 may have a slight curve corresponding with the curve of thering portion 34, as illustrated in FIG. 16. In another embodiment of theinvention, as illustrated in FIG. 17, the elongated mount beam 52 may beconfigured to be mechanically attached to the ring portion 34 of theintermediate structure 16.

As illustrated in FIGS. 16-17, the intermediate structure 16 may alsocomprise one or more support links 56 extending from the mount beam 52and configured to join the ring portion 34 with the mount beam 52 and/orto join the mount beam 52 with the engine core 14. For example, twosupport links 56 may extend from the mount beam 52 at or proximate to afirst end 58 of the mount beam 52 substantially opposite of a second end60 of the mount beam 52 at which the ring portion 34 is attached. Thesupport links 56 at the first end 58 of the mount beam 52 may be angledslightly away from each other and may be substantially parallel with theflanges 40,42 or edges 38,36 of the ring portion 34, as illustrated inFIG. 16. Furthermore, some support links 56 may extend from a pointbetween the first end 58 of the mount beam 52 and the second end 60 ofthe mount beam 52 to the engine core 14 and/or the ring portion 34 ofthe intermediate structure 16. Finally, support links 56 may extend fromthe mount beam 52 at or proximate to the second end 60 of the mount beam52 and be configured to attach the mount beam 52 to the ring portion 34of the intermediate structure 16, as illustrated in FIG. 17.

The ring portion 34, mount beam 52, and any of the support links 56 maybe fastened or welded together and/or constructed as a single casting ormultiple castings joined together. Furthermore, the intermediatestructure 16 may be constructed as a fastened assembly consisting ofinternal frames and bulkheads covered by stressed skins or composites.In general, the intermediate structure 16 and/or the components thereofmay be configured to react to combined loads of the engine core 14 andthe fan module 12.

The intermediate structure 16 may be configured for fixedly attaching tothe pylon 18 of the aircraft. Specifically, the ring portion 34 and/orthe mount beam 52 may be detachably or permanently attached to orintegrally formed with the pylon 18 (i.e., monolithic, one-piececonstruction). For example the intermediate structure 16 may compriseattachment features configured for attaching the ring portion 34 and/orthe mount beam 52 to the pylon 18. In various embodiments of theinvention, the mount beam 52 may be integrally formed with the pylon 18,mechanically fastened to the pylon 18 using bolts or other mechanical,detachable fasteners, and/or otherwise mounted to the pylon 18 using anycombination of attachment methods. The ring portion 34, fixed to thesecond end 60 of the mount beam 52, may be fixed relative to the pylon18 via the mount beam 52 and/or directly fixed to the pylon 18. Forexample, the ring portion 34 may be fixed to the pylon 18 by integrallyforming the ring portion 34 and the pylon 18, mechanically fastening thering portion 34 to the pylon 18, and/or otherwise mounting the ringportion 34 to the pylon 18 using any combination of attachment methods.Note that any portion of the intermediate structure 16 may alternativelybe mounted to another portion of the airframe without departing from thescope of the invention.

In some embodiments of the propulsion system 10, such as the “pusher”configuration noted above, the intermediate structure 16 or ring portion34 thereof may be configured with passageways to allow driving exhaustgases to move from a gas turbine exit of the engine core 14 to anentrance of a gas-powered embodiment of the fan module 12. A similarconfiguration may be used to allow passage of exhaust gasses from theengine core turbine to the primary exhaust. The intermediate structure16 may also be configured to be compatible with shaft-driven propulsionsystems.

The intermediate structure 16 may further comprise or have mountedthereto at least one gearbox 62, such as a speed reduction gearbox orvarious accessory gearboxes, as illustrated in FIGS. 7-10. For example,a shaft-driven propulsion system may connect a shaft of the engine core14 with the fan module 12 via a speed reduction gearbox mounted to andsupported by the intermediate structure 16 or the ring portion thereof.The speed reduction gearbox may allow the rotation speeds of the enginecore 14 and fan module 12 to be optimized independently. In someembodiments of the invention, the speed reduction gearbox may be anintegral part of the intermediate structure 16. Alternatively, the speedreduction gearbox may be supported by the engine core 14 or the fanmodule 12.

The gearbox 62 may also include an engine accessory gearbox integratedwith, fixed to, and/or supported by the intermediate structure 16. Theengine accessory gearbox may be configured to accept shaft horsepowerfrom the engine core and, through a series of gears, provide rotarypower to accessories mounted to the engine accessory gearbox.Accessories may include aircraft power generators and hydraulic pumps,as well as engine-dedicated fuel pumps, hydraulic pumps, and generators.An engine accessory gearbox independent from the engine core 14 (i.e.,supported by the intermediate structure 16) may require fewer serviceconnections to be broken to remove the engine core 14 or fan module 12.The intermediate structure-mounted engine accessory gearbox may bedriven through an inline power take-off gearbox also supported by theintermediate structure 16.

The gearbox 62 or gearboxes of the propulsion system 10 may be dividedbetween engine-dedicated accessories and those for the aircraft. In someembodiments of the invention, aircraft accessories and gearboxes may besupported by and/or integrated with the intermediate structure 16, whileengine-dedicated accessories may be driven by an engine core-mountedgearbox.

In use, the fan module 12 may be bolted to the intermediate structure 16independently of the engine core 14. For example, the mountingprovisions 30 of the fan module 12 may be bolted or otherwise attachedto the first flange 40 of the ring portion 34 and the mountingprovisions 32 of the engine core 14 may be bolted or otherwise attachedto the second flange 42 of the ring portion 34. To remove just theengine core 14, the engine core 14 may be unbolted or unattached fromthe intermediate structure 16 while the fan module 12 remains bolted tothe intermediate structure 16. Furthermore, the support links 56 mayalso be disconnected from the engine core 14. To remove just the fanmodule 12, the fan module 12 may be unbolted or unattached from theintermediate structure 16 while the fan module 12 remains bolted to theintermediate structure 16. During removal of the fan module 12 and/orthe engine core 14, one or more connections to the gearboxes 62 attachedto the intermediate structure 16 may need to be disconnected.

The present invention provides a number of advantages over the priorart. Specifically, the intermediate structure 16 allows installationand/or removal of either the fan module 12 or the engine core 14 withoutadditional supporting or bracing ground support equipment (GSE).However, if needed, GSE attachments for lowering or raising the enginecore 14 or fan module 12 may be added to the intermediate structure 16.Furthermore, handling of the fan module 12 and engine core 14independently is easier, since less mass and volume is required to beraised, lowered, or positioned. In some embodiments of the invention,pre-assembly of the intermediate structure 16, the engine core 14, andthe fan module 12 would allow the propulsion system 10 to be installedon the pylon 18 as a unit, if desired. This could be beneficial tooriginal equipment manufacturers (OEM) during an initial build of anaircraft to shorten installation time. Another advantage of the presentinvention is that the ring portion 34 transmits torque from the fanmodule 12 directly to the pylon 18 or airframe, so that the engine core14 does not have to be built to accommodate for the torque from the fanmodule 12.

The present invention may also allow for standardized engine mountingflanges on the ring portion 34, such that different engine cores and fanmodules may be joined with each other. This allows for competition thatis not necessarily tied to the engine core 14. It may be possible tohave a single fan module or rotor design for the airframe with acustomer option for which gas generator or engine core is used to drivethe fan module 12.

Another advantage of the present invention is the integration of theaccessory gearbox and/or the fan speed reduction gearbox with theintermediate structure 16. This reduces the number of connectionsbetween the engine core 14 and the aircraft that must be disconnectedprior to engine core removal and removes the suspended mass of theinstallation from the engine core 14. Since the mass of the accessorygearbox is not placed on the engine core 14, engine case distortion andsubsequent performance penalties are reduced. Incorporation of the fanspeed reduction gearbox between the fan module 12 and the engine core 14allows each of the components' rotational speeds to be optimizedindependently. Because it is part of the intermediate structure 16, thecantilevered mass of the gearbox 62 can be reduced over that of agearbox included as part of the fan module 12.

Although the invention has been described with reference to thepreferred embodiment illustrated in the attached drawing figures, it isnoted that equivalents may be employed and substitutions made hereinwithout departing from the scope of the invention as recited in theclaims.

Having thus described various embodiments of the invention, what isclaimed as new and desired to be protected by Letters Patent includesthe following:
 1. A method of coupling and decoupling an engine corewith an engine fan module via an intermediate structure of an aircraft,the method comprising: mechanically attaching the engine core to theintermediate structure at a first edge of the intermediate structure,wherein the intermediate structure has a ring-shaped portion that isrigid and is mounted directly to a pylon or airframe of the aircraft;mechanically attaching the engine fan module to the intermediatestructure at a second edge of the intermediate structure, wherein thesecond edge of the intermediate structure is opposite of the first edge;and mechanically disconnecting and removing one of the engine core andthe engine fan module from the intermediate structure while another oneof the engine core and the engine fan module remains mechanicallyattached to and supported on the aircraft by the intermediate structure.2. The method of claim 1, wherein the step of mechanically disconnectingand removing comprises disconnecting and removing the engine core fromthe intermediate structure while the engine fan module remainsmechanically attached to and supported on the aircraft by theintermediate structure.
 3. The method of claim 1, wherein the step ofmechanically disconnecting and removing comprises disconnecting andremoving the engine fan module from the intermediate structure while theengine core remains mechanically attached to and supported on theaircraft by the intermediate structure.
 4. The method of claim 1,wherein a fan speed reduction gearbox is mounted to the intermediatestructure, wherein the steps of mechanically attaching the engine coreand the fan module to the intermediate structure further compriseattaching rotary components of the engine core and the engine fan modulewith rotary components of the fan speed reduction gearbox mounted to theintermediate structure, wherein the fan speed reduction gearbox isconfigured for compensating for a difference in rotary speed between theengine core and the fan module.
 5. The method of claim 1, wherein theintermediate structure further comprises an elongated mount beam havinga first end integrally formed with the ring-shaped portion at the firstedge or the second edge and a second end opposite of the first end. 6.The method of claim 5, further comprising attaching the engine core tothe second end of the elongated mount beam to structurally support theengine core.
 7. The method of claim 1, wherein an accessory gearbox ismounted to the intermediate structure, wherein the steps of mechanicallyattaching the engine core and the fan module to the intermediatestructure further comprising attaching rotary components of the enginecore and the engine fan module with rotary components of the accessorygearbox, wherein the accessory gearbox is configured to provide rotarypower from the engine core or the fan module to other accessories of theaircraft.
 8. A method of coupling and decoupling an engine core with anengine fan module via an intermediate structure of an aircraft, themethod comprising: mechanically attaching the engine core to aring-shaped portion of the intermediate structure at a first edge of thering-shaped portion, wherein the ring-shaped portion is rigid, whereinthe intermediate structure further includes an elongated mount beamhaving a first end integrally formed with the ring-shaped portion and asecond end opposite of the first end, wherein the intermediate structureis mounted directly to a pylon or airframe of the aircraft; mechanicallyattaching the engine fan module to the ring-shaped portion at a secondedge of the ring-shaped portion, wherein the second edge is opposite ofthe first edge; and mechanically disconnecting and removing the enginecore from the intermediate structure while the engine fan module remainsmechanically attached to and supported on the aircraft by theintermediate structure; or mechanically disconnecting and removing theengine fan module from the intermediate structure while the engine coreremains mechanically attached to and supported on the aircraft by theintermediate structure.
 9. The method of claim 8, wherein a fan speedreduction gearbox is mounted to the intermediate structure, wherein thesteps of mechanically attaching the engine core and the fan module tothe intermediate structure further comprise attaching rotary componentsof the engine core and the engine fan module with rotary components ofthe fan speed reduction gearbox mounted to the intermediate structure,wherein the fan speed reduction gearbox is configured for compensatingfor a difference in rotary speed between the engine core and the fanmodule.
 10. The method of claim 8, further comprising attaching theengine core to the second end of the elongated mount beam tostructurally support the engine core.
 11. The method of claim 8, whereinan accessory gearbox is mounted to the intermediate structure, whereinthe steps of mechanically attaching the engine core and the fan moduleto the intermediate structure further comprising attaching rotarycomponents of the engine core and the engine fan module with rotarycomponents of the accessory gearbox, wherein the accessory gearbox isconfigured to provide rotary power from the engine core or the fanmodule to other accessories of the aircraft.
 12. The method of claim 8,wherein the intermediate structure further comprises a first attachmentflange extending from the ring-shaped portion at the first edge and asecond attachment flange extending from the ring-shaped portion at thesecond edge, wherein the step of mechanically attaching the engine coreto the ring-shaped portion comprises mechanically attaching the enginecore to the first attachment flange, wherein the step of mechanicallyattaching the engine fan module to the ring-shaped portion comprisesmechanically attaching the engine fan module to the second attachmentflange.
 13. The method of claim 12, wherein mechanically attachingincludes bolting portions of the engine core and the engine fan moduleto the first and second attachment flanges, respectively.
 14. The methodof claim 8, further comprising attaching one or more support linksextending from the second end of the mount beam to the engine core. 15.The method of claim 8, wherein the mount beam further comprises asubstantially tapering section extending from the first edge of thering-shaped portion to a point between the first and second ends of theelongated mount beam, wherein the substantially tapering section tapersin a direction away from the first end of the mount beam.
 16. The methodof claim 8, further comprising attaching at least one support link fromthe mount beam to the ring portion and at least one support link fromthe second end of the mount beam to the engine core.
 17. A method ofcoupling and decoupling an engine core with an engine fan module via anintermediate structure of an aircraft, the method comprising:mechanically attaching the engine core to a ring-shaped portion of theintermediate structure at a first edge of the ring-shaped portion,wherein the ring-shaped portion is rigid; mechanically attaching theengine fan module to the ring-shaped portion at a second edge of thering-shaped portion, wherein the second edge is opposite of the firstedge; attaching the engine core to a second end of an elongated mountbeam of the intermediate structure to structurally support the enginecore, wherein the elongated mount beam has a first end integrally formedwith the ring-shaped portion and the second end opposite of the firstend, wherein the intermediate structure is mounted directly to a pylonor airframe of the aircraft; and mechanically disconnecting and removingthe engine core from the ring-shaped portion and the elongated mountbeam while the engine fan module remains mechanically attached to thering-shaped portion and thus supported on the aircraft by theintermediate structure; or mechanically disconnecting and removing theengine fan module from the ring-shaped portion while the engine coreremains mechanically attached to the ring-shaped portion and theelongated mount beam and thus supported on the aircraft by theintermediate structure.
 18. The method of claim 17, wherein a fan speedreduction gearbox is mounted to the intermediate structure, wherein thesteps of mechanically attaching the engine core and the fan module tothe intermediate structure further comprise attaching rotary componentsof the engine core and the engine fan module with rotary components ofthe fan speed reduction gearbox mounted to the intermediate structure,wherein the fan speed reduction gearbox is configured for compensatingfor a difference in rotary speed between the engine core and the fanmodule.
 19. The method of claim 17, wherein an accessory gearbox ismounted to the intermediate structure, wherein the steps of mechanicallyattaching the engine core and the fan module to the intermediatestructure further comprising attaching rotary components of the enginecore and the engine fan module with rotary components of the accessorygearbox, wherein the accessory gearbox is configured to provide rotarypower from the engine core or the fan module to other accessories of theaircraft.
 20. The method of claim 17, wherein the intermediate structurefurther comprises a first attachment flange extending from thering-shaped portion at the first edge and a second attachment flangeextending from the ring-shaped portion at the second edge, wherein thestep of mechanically attaching the engine core to the ring-shapedportion comprises bolting portions of the engine core to the firstattachment flange, wherein the step of mechanically attaching the enginefan module to the ring-shaped portion comprises bolting portions of theengine fan module to the second attachment flange.